EP3992086B1 - Flugzeug und verfahren zum betrieb davon - Google Patents

Flugzeug und verfahren zum betrieb davon Download PDF

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Publication number
EP3992086B1
EP3992086B1 EP21206298.8A EP21206298A EP3992086B1 EP 3992086 B1 EP3992086 B1 EP 3992086B1 EP 21206298 A EP21206298 A EP 21206298A EP 3992086 B1 EP3992086 B1 EP 3992086B1
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EP
European Patent Office
Prior art keywords
engine
thrust
compressed gas
aircraft
wing
Prior art date
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EP21206298.8A
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English (en)
French (fr)
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EP3992086A1 (de
Inventor
Santo Chiappetta
David H. Menheere
Timothy Redford
Daniel VAN DEN ENDE
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Pratt and Whitney Canada Corp
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Pratt and Whitney Canada Corp
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/16—Aircraft characterised by the type or position of power plants of jet type
    • B64D27/18—Aircraft characterised by the type or position of power plants of jet type within, or attached to, wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C15/00—Attitude, flight direction, or altitude control by jet reaction
    • B64C15/02—Attitude, flight direction, or altitude control by jet reaction the jets being propulsion jets
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/04—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
    • B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
    • B64C21/04—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for blowing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • F05D2260/606—Bypassing the fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/80—Diagnostics
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/05—Purpose of the control system to affect the output of the engine
    • F05D2270/051—Thrust
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/09—Purpose of the control system to cope with emergencies
    • F05D2270/093—Purpose of the control system to cope with emergencies of one engine in a multi-engine system
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/335—Output power or torque
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the application relates generally to aircrafts and, more particularly, to the propulsion and stabilisation systems thereof.
  • Engine failure in the case of a twin-engine aircraft, for instance, leads to a scenario where the operating engine generates torque around the center of gravity of the aircraft, which can induce yaw.
  • the torque corresponds to the thrust (force) generated by the operating engine times the distance with the center of gravity of the aircraft.
  • torque can be compensated using a tail rudder, but ensuring that the tail rudder will be able to compensate for this torque may require oversizing the tail rudder compared to the size it would otherwise require, leading, amongst other potentially undesirable aspects, to additional weight. There always remains room for improvement.
  • US 3173628 A discloses a prior art aircraft.
  • Fig. 1 illustrates an example of a turbine engine.
  • the turbine engine 10 is a turboprop engine generally comprising in serial flow communication, a compressor section 12 for pressurizing the air, a combustor section 14 in which the compressed air is mixed with fuel and ignited for generating an annular stream of hot combustion gases around the engine axis 11, and a turbine section 16 for extracting energy from the combustion gases.
  • the turbine engine 10 terminates in an exhaust section 19.
  • the turboshaft engine 10 has two compressor and turbine stages, including a high pressure stage associated to a high pressure shaft 20, and a low pressure stage associated to a low pressure shaft 22.
  • the low pressure shaft 22 is used as a power source for a propeller during use.
  • Turboprop engines typically have some form of gearing by which the power of the low pressure shaft 22 is transferred to an external shaft 26 bearing blades or propeller. This gearing, which can be referred to as a gearbox 24 for the sake of simplicity, typically reduces the rotation speed to reach an external rotation speed which is better adapted to rotate the blades or propeller for instance.
  • Turbofans are another common type of aircraft engine. Instead of using a propeller, turbofans typically have a fan extending across a bypass duct, the bypass duct extending around the core gas path.
  • the fan can be driven using a lower pressure turbine stage, for instance, while the compressor can be driven using a higher pressure turbine stage, via a concentric shaft arrangement.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (14)

  1. Verfahren zum Betreiben eines Luftfahrzeugs (30), das ein erstes Triebwerk (32), das an einem ersten Flügel (36) auf einer ersten Seite eines Rumpfes (42) befestigt ist, und ein zweites Triebwerk (34), das an einem zweiten Flügel (44) auf einer zweiten Seite des Rumpfes (42) befestigt ist, aufweist, wobei der zweite Flügel (44) ein proximales Ende (46), das an dem Rumpf (42) befestigt ist, und ein distales Ende (48), das sich von dem Rumpf (42) weg erstreckt, aufweist, wobei das Verfahren Folgendes umfasst:
    Betreiben des ersten Triebwerks (32), um ein Gierdrehmoment um einen Schwerpunkt (G) des Luftfahrzeugs (30) herum zu erzeugen,
    während des Betreibens des ersten Triebwerks (32), Leiten von Druckgas von dem ersten Triebwerk (32) zu einer Schuberzeugungsvorrichtung (54), die sich an dem distalen Ende (48) des zweiten Flügels (44) befindet, und
    wobei die Schuberzeugungsvorrichtung (54) unter Verwendung der Energie des Druckgases Schub erzeugt, um das von dem ersten Triebwerk (32) erzeugte Gierdrehmoment auszugleichen;
    wobei das erste Triebwerk (32) einen Verdichterabschnitt (12), einen Brennkammerabschnitt (14), einen Turbinenabschnitt (16) und einen Abgaskanal (19) in sequenzieller Fluidströmungsverbindung aufweist, dadurch gekennzeichnet, dass
    die Druckgasquelle Abgas aus dem Abgaskanal (19) ist.
  2. Verfahren nach Anspruch 1, wobei das Erzeugen von Schub ein Ausdehnen des Druckgases in einer Strahldüse der Schuberzeugungsvorrichtung (54) beinhaltet.
  3. Verfahren nach Anspruch 1 oder 2, wobei das Erzeugen von Schub ein Ausdehnen des Druckgases in einer Turbine der Schuberzeugungsvorrichtung (54) beinhaltet, wobei die Turbine einen Verdichter oder einen Propeller antreibt.
  4. Verfahren nach einem der vorhergehenden Ansprüche, ferner umfassend Aufheben des Gierdrehmoments durch ein durch den Schub der Schuberzeugungsvorrichtung (54) erzeugtes Gegendrehmoment.
  5. Verfahren nach einem der vorhergehenden Ansprüche, umfassend Erzeugen des Schubs, während das zweite Triebwerk (34) nicht in Betrieb ist.
  6. Verfahren nach einem der Ansprüche 1 bis 4, ferner umfassend, während des Betreibens des ersten Triebwerks (32) und Erzeugens des Schubs, wobei die Schuberzeugungsvorrichtung (54) eine erste Schuberzeugungsvorrichtung ist, Betreiben des zweiten Triebwerks (34), Leiten von Druckgas von dem zweiten Triebwerk (34) zu einer zweiten Schuberzeugungsvorrichtung (56), die sich an einem distalen Ende (40) des ersten Flügels (36) befindet, und die zweite Schuberzeugungsvorrichtung (56) unter Verwendung der Energie des Druckgases Schub erzeugt.
  7. Verfahren nach einem der vorhergehenden Ansprüche, ferner umfassend Öffnen eines Durchgangs (58), der das Druckgas in Abhängigkeit vom Erkennen einer Fehlfunktion des zweiten Triebwerks (34) leitet.
  8. Luftfahrzeug (30), das Folgendes aufweist:
    einen Rumpf (42);
    einen ersten Flügel (36), der sich auf einer ersten Seite des Rumpfes (42) von einem proximalen Ende (38) zu einem distalen Ende (40) erstreckt;
    einen zweiten Flügel (44), der sich auf einer zweiten Seite des Rumpfes (42) von einem proximalen Ende (46) zu einem distalen Ende (48) erstreckt;
    ein erstes Triebwerk (32), das durch den ersten Flügel (36) getragen wird;
    ein zweites Triebwerk (34), das durch den zweiten Flügel (44) getragen wird, wobei jedes des ersten und des zweiten Triebwerks (32, 34) durch eine Abstandsstrecke (d) von einem Schwerpunkt (G) des Luftfahrzeugs (30) getrennt ist und dazu konfiguriert ist, während des Betriebs ein Gierdrehmoment in entgegengesetzte Richtungen zu erzeugen;
    eine erste Schuberzeugungsvorrichtung (54), die sich an dem distalen Ende (48) des zweiten Flügels (44) befindet;
    eine zweite Schuberzeugungsvorrichtung (56), die sich an dem distalen Ende (40) des ersten Flügels (36) befindet;
    einen ersten Druckgasdurchlass (58), der sich von dem ersten Triebwerk (32) zu der ersten Schuberzeugungsvorrichtung (54) erstreckt;
    einen zweiten Druckgasdurchlass (60), der sich von dem zweiten Triebwerk (34) zu der zweiten Schuberzeugungsvorrichtung (56) erstreckt;
    wobei die erste und die zweite Schuberzeugungsvorrichtung (54, 56) dazu konfiguriert sind, Schub unter Verwendung von Energie aus der Ausdehnung von Druckgas zu erzeugen, das aus dem entsprechenden Druckgasdurchlass (58, 60) aufgenommen wird, um das durch das entsprechende Triebwerk (32, 34) erzeugte Gierdrehmoment auszugleichen,
    wobei jedes des ersten Triebwerks (32) und des zweiten Triebwerks (34) in sequenzieller Fluidströmungsverbindung einen Verdichterabschnitt (12), einen Brennkammerabschnitt (14), einen Turbinenabschnitt (16) und einen Abgasabschnitt (19) aufweist, dadurch gekennzeichnet, dass
    der erste und der zweite Druckgasdurchgang (58, 60) jeweils eine Einlassöffnung aufweisen, die mit dem Abgasabschnitt (19) des jeweiligen Triebwerks (32, 34) fluidverbunden ist.
  9. Luftfahrzeug (30) nach Anspruch 8, wobei sich der erste und der zweite Druckgasdurchgang (58, 60) voneinander unterscheiden.
  10. Luftfahrzeug (30) nach Anspruch 8 oder 9, wobei der erste und der zweite Druckgasdurchgang (58, 60) ein gemeinsames Segment (62), das sich zwischen dem ersten und dem zweiten Triebwerk (32, 34) erstreckt, spezielle Segmente und Ventile (64, 66) aufweisen, wobei die Ventile (64, 66) betreibbar sind, um die speziellen Segmente, die einem des ersten und des zweiten Druckgasdurchgangs (58, 60) zugeordnet sind, selektiv von dem gemeinsamen Segment (62) aus zu schließen.
  11. Luftfahrzeug (30) nach Anspruch 8, 9 oder 10, wobei sich die erste und die zweite Schuberzeugungsvorrichtung (54, 56) an der Flügelspitze (52, 50) der entsprechenden Flügel (44, 36) befinden.
  12. Luftfahrzeug (30) nach einem der Ansprüche 8 bis 11, wobei das erste Triebwerk und das zweite Triebwerk (32, 34) Doppeltriebwerke sind.
  13. Luftfahrzeug (30) nach einem der Ansprüche 8 bis 12, wobei die erste und die zweite Schuberzeugungsvorrichtung (54, 56) Strahldüsen sind.
  14. Luftfahrzeug (30) nach einem der Ansprüche 8 bis 12, wobei die erste und die zweite Schuberzeugungsvorrichtung (54, 56) jeweils eine Turbine aufweisen, die mit einem Propeller oder Gebläse verbunden ist.
EP21206298.8A 2020-11-03 2021-11-03 Flugzeug und verfahren zum betrieb davon Active EP3992086B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US17/088,128 US11585280B2 (en) 2020-11-03 2020-11-03 Aircraft and method of operating same

Publications (2)

Publication Number Publication Date
EP3992086A1 EP3992086A1 (de) 2022-05-04
EP3992086B1 true EP3992086B1 (de) 2024-07-10

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US (1) US11585280B2 (de)
EP (1) EP3992086B1 (de)
CA (1) CA3129994A1 (de)

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3154917A (en) * 1963-04-15 1964-11-03 Ryan Aeronautical Co Diverter for ducted fan aircraft
US3173628A (en) 1963-08-05 1965-03-16 Bristol Siddeley Engines Ltd Aircraft having gas-turbine jet propulsion and sustentation engines
US3387457A (en) * 1965-03-01 1968-06-11 George H. Garraway Combined turbojet and turboprop engine
FR2044695B1 (de) * 1969-03-08 1974-05-24 Rolls Royce
US4589611A (en) 1983-03-01 1986-05-20 Maurice Ramme Air jet reaction contrarotating rotor gyrodyne
US6729575B2 (en) * 2002-04-01 2004-05-04 Lockheed Martin Corporation Propulsion system for a vertical and short takeoff and landing aircraft
FR2914075B1 (fr) * 2007-03-22 2009-04-24 Airbus France Sas Procede et dispositif de limitation de la commande de roulis d'un aeronef en fonction d'une dissymetrie de poussee
RU2494920C1 (ru) 2012-11-06 2013-10-10 Юлия Алексеевна Щепочкина Крыло летательного аппарата
US10227138B2 (en) 2016-03-04 2019-03-12 Embraer S.A. Asymmetry-proof multi-engine aircraft
US10005561B2 (en) * 2016-06-16 2018-06-26 Ge Aviation Systems Llc Controlling aircraft using thrust differential trim

Also Published As

Publication number Publication date
US20220136448A1 (en) 2022-05-05
CA3129994A1 (en) 2022-05-03
US11585280B2 (en) 2023-02-21
EP3992086A1 (de) 2022-05-04

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